EP1657545B1 - Method for detecting substructure - Google Patents
Method for detecting substructure Download PDFInfo
- Publication number
- EP1657545B1 EP1657545B1 EP05077399.3A EP05077399A EP1657545B1 EP 1657545 B1 EP1657545 B1 EP 1657545B1 EP 05077399 A EP05077399 A EP 05077399A EP 1657545 B1 EP1657545 B1 EP 1657545B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- substructure
- scanning
- probe
- assembly
- probe positioner
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Not-in-force
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/72—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables
- G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
- G01N27/90—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
- G01N27/9013—Arrangements for scanning
- G01N27/902—Arrangements for scanning by moving the sensors
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/26—Scanned objects
- G01N2291/269—Various geometry objects
- G01N2291/2694—Wings or other aircraft parts
Definitions
- the present invention generally relates to nondestructive inspection methods and, more particularly, to detecting substructure using precision eddy current scanning.
- Automated assembly systems in the aerospace industry for example, for airframe assembly of aircraft, generally employ some type of vision system for locating structure components and key features of components, such as edges of flanges, machined steps, and tooling holes. Knowledge of the exact location of these features is necessary, since these features are used to adjust numerically controlled programs for drilling holes or other machining operations, such as trimming or reaming, to maintain blueprint tolerances.
- the outer mold line skins are temporarily fastened to the structure and the created map of the substructure needs to be transferred to the skin. Since this step is performed while the assembly is in the machine bed, the flow time is impacted and the percentage of the machine time actually used for the intended function, such as drilling, is reduced.
- Eddy current as a nondestructive inspection process is commonly used in the aerospace industry to detect subsurface flaws or anomalies in conductive materials.
- the advantage of eddy current for nondestructive inspection is the ability to perform scanning through the outer skin material.
- Eddy current data can be collected using automated scanning systems to improve the quality of the measurements and to construct images of scanned areas.
- the most common type of scanning is line scanning where an automated system is used to push the probe at a fixed speed.
- the data is usually presented as a strip chart recording.
- the advantage of using a linear scanning system is that the probe is moved at a constant speed such that an indication on the strip chart can be correlated to a position on the part being scanned.
- Two-dimensional scanning systems are used to scan a two-dimensional area.
- the data is typically displayed in a C -scan, which is a false-color plot of signal strength or phase angle shift as a function of position.
- Mobile automated scanners such as MAUSĀ® IV and V developed by The Boeing Company, St. Louis, are generally used in the aerospace industry for nondestructive testing utilizing eddy current and ultrasonic waves.
- MAUS IV eddy current C-scans are used, for example, for corrosion detection or crack detection around fastener holes.
- US 2003/192382 A1 discloses an apparatus that examines the internal structure of an object which reflects acoustic signals in the 1-200 MHz frequency range.
- the apparatus has an acoustic transducer that emits and receives the acoustic signals and an acoustic coupler to couple the transducer to the object, and the apparatus may scan over the surface of the object.
- US 2,785,592 discloses a magnetic position location and controlling probe and system.
- For the magnetic position location sensing coils are used. Eddy current is generated in plate material.
- US 2003/0212489 A1 discloses a magnetic indexer for locating a device producing a magnetic field in a blind or inaccessible position of a work piece.
- a device comprising a plurality of probes is positioned on a surface of the work piece and senses the magnetic field produced by the device in the blind or inaccessible position of the work piece.
- US 5,833,799 discloses an apparatus for thermoplastic welding together by fusing bonding an assembly of composite parts.
- the apparatus includes a weld skate having induction work coil and two pressure pads, one on each side of the coil in its direction of motion in operation.
- the present invention has for its object to improve upon the above prior art apparatus.
- the present invention provides a method for detecting substructure, comprising the steps of non-destructively scanning an assembly (37) using a substructure scanning system (100) including a precision motion carriage (10), a first probe positioner movably coupled to said precision motion carriage such that it can move in a first direction relative to said precision motion carriage, a second probe positioner located above said first probe positioner and movably coupled to said precision motion carriage such that it can move in a second direction relative to said precision motion carriage, and a non-destructive scanning sensor (11) located in an opening of said first probe positioner and in an opening of said second probe positioner of said precision motion carriage; positioning said assembly (37) including a substructure (38) covered with an outer skin (39) under said substructure scanning system (100); positioning said scanning sensor (11) on said outer skin (39) of said assembly (37); moving said scanning sensor (11) over said outer skin (39) with said first probe positioner and said second probe positioner of said precision motion carriage (10), wherein moving said scanning sensor is accomplished by moving said first probe positioner and/or said second probe
- the present invention provides for precisely detecting substructure using precision eddy current scanning.
- the present invention further uses a precision motion carriage that enables the location of substructure features within the engineering tolerances required.
- the present invention still further provides a method for the location of substructure features through an outer panel with sufficient accuracy to control assembly operations that may be used for, but is not limited to, the location of substructure features, such as edges of flanges, machined steps, or tooling holes, covered by outer mold line skins of an aircraft airframe.
- the substructure can be detected by any eddy current by sufficient accuracy to control assembly apparatus and meet engineering tolerances.
- the present invention provides for detecting substructure using nondestructive techniques. Contrary to the known prior art, an outer panel does not need to be removed to scan substructure that lies underneath the panel. Furthermore, by using the method for detecting substructure according to one embodiment of the present invention, substructure features can be located through the skin of a structure with sufficient accuracy to control assembly operations and meet engineering tolerances, which is not possible using prior art handheld devices or prior art nondestructive techniques.
- the method for detecting substructure as in one embodiment of the present invention may be used in the aerospace industry, for example, in the airframe assembly of aircraft.
- the method for detecting substructure further enables detection and location of substructure features, such as edges of flanges, machined steps, or tooling holes, that are located underneath the outer mold line skins, for example, of a fuselage or a wing of an aircraft.
- the present invention uses eddy current to scan the outer mold line skin of an aircraft in order to detect substructure features underneath the skin. Since the removal of the skin is no longer required to create a map of the substructure, the steps of removing and refastening the skin, as currently needed using prior art methods, can be eliminated. Furthermore, by using eddy current for scanning a solid sheet of metallic or nonmetallic material, such as an aircraft airframe skin, edges and other features of metallic substructure located underneath the skin, on the side of the skin opposite to the scanning probe, can be located without removal of the airframe skin and in a nondestructive process. The advantage of eddy current for scanning is its ability to perform the scanning through the outer skin material.
- the present invention uses a precision motion carriage that enables application of the eddy current scanning process with a high accuracy.
- the precision motion carriage as in one embodiment of the present invention, substructure features can be located with sufficient accuracy to control assembly operations, for example, numerically controlled programs for drilling holes, for trimming, or for reaming, and to meet engineering tolerances.
- prior art hand-held devices for detecting substructure does not provide this accuracy.
- An illustrative example provides a gantry motion system that moves the scanning sensor precisely over an area to be examined.
- a robot motion system moves the scanning sensor precisely over an area to be examined.
- Both motion systems enable the integration of the eddy current scanning process into numerically controlled machines, such as numerically controlled drilling machines, and, therefore, reduce the machine bed low time.
- the integration of the scanning process into the numerically controlled machining process enables instant machine coordinate correction without the need for manual actions, which provides more flexibility in the assembly process than prior art methods where the skins needs to be removed before the substructure features are visible, and where a map of the substructure needs to be created manually.
- the product flow and automation of aircraft assemblies can be improved and the need for subassemblies and components can be reduced in comparison with prior art methods for locating substructure.
- the dependent scanning system 100 may include a precision motion carriage 10, a probe 11, a controller box 17, and a computer interface 18.
- the dependent scanning system 100 may be used as a substructure scanning system.
- the dependent scanning system 100 may enable application of eddy current scanning with a high accuracy.
- the dependent scanning system 100 may be used as an attachment to an existing assembly machine, such as a machine executing numerically controlled operations, such as drilling, trimming, routing, machining or reaming.
- the assembly machine may locate the dependent scanning system 100 on a surface, for example, of a fuselage outer skin 31 ( Figure 3 ), where the dependent scanning system 100 may perform the final precision scan in an x (122)-y (132) raster mode.
- the precision motion carriage 10 may include a probe positioner 12, a probe positioner 13, and a frame 14.
- the frame 14 may have the shape of a square and may enclose a two-dimensional area 16.
- the probe positioner 12 may extend across the frame 14 in x-direction 122.
- the probe positioner 12 may include an opening 121 for guiding the probe 11.
- the probe positioner 12 may be inserted into the frame 14 such that it may be moved in y-direction 132, within the frame 14.
- the probe positioner 13 may extend across the frame 14 in y-direction 132.
- the probe positioner 13 may include an opening 131 for guiding the probe 11.
- the probe positioner 13 may be inserted in the frame 14 on top of the probe positioner 12 and in a right angle to the probe positioner 12.
- the probe positioner 13 may be moved in x-direction 122 within the frame 14.
- the opening 131 and the opening 121 form a window 15.
- the probe 11 may be inserted in the window 15.
- the probe 11 may be moved precisely over the area 16 enclosed by the frame 14. By inserting the probe 11 into the window 15, the probe 11 may be accurately indexed.
- the probe 11 may be moved to scan a two-dimensional area 16 in an x (122)-y (132) raster mode.
- the probe 11 may be further moved within the opening 121 in x-direction 122 for one-dimensional line scanning.
- the probe 11 may still further be moved within the opening 131 in y-direction 132 for one-dimensional line scanning.
- the probe 11 may be an eddy current scanning sensor that may be used to detect metallic features of a substructure 38 underneath an outer skin 39 ( Figures 3 and 4 ), as frequently needed, for example, during the aircraft airframe assembly.
- the probe 11 may further be an ultrasonic scanning sensor that may be used to detect nonmetallic features of a substructure 38 underneath an outer skin 39 ( Figures 3 and 4 ).
- the probe 11 may further be any nondestructive scanning sensor.
- Using the precision motion carriage 10 for scanning an assembly such as test assembly 20 ( Figures 2a and 2b ) or the assembly 37 ( Figures 3 and 4 ), may minimize changes in liftoff or fill factor resulting from probe 11 wobble or uneven surfaces, may provide repeatability of scanning results and high resolution mapping.
- the probe 11 may be connected with a computer interface 18 via a controller box 17.
- the controller box 17 may provide an alternating current to the probe 11.
- the probe 11 may generate eddy currents and sense changes in the eddy current field.
- the controller box 17 may receive signals that indicate changes in the eddy current and supply these signals to the computer interface 18.
- the computer interface 18 may include scanning control software 181 and signal processing software 182.
- the computer interface 18 may be connected with a keyboard 183.
- the probe positioner 12 and the probe positioner 13 may be connected with the computer interface 18.
- the scanning control software 181 may control the movement of the probe positioner 12 and the probe positioner 13 and, therefore, of the probe 11.
- the signal processing software 182 may generate an image (such as the C-scan 25, Figure 2c ) of the substructure 38 ( Figures 3 and 4 ).
- the signal processing software 182 may generate a C-scan 25 (as shown in Figure 2c ) if a two-dimensional area 16 was scanned in an x (122)- y (132) raster mode.
- the C-scan 25 may be a false-color plot of signal strength or phase angle shift as a function of the position of the probe 11.
- the signal processing software 182 may generate a strip chart if a line scan in x (122) or y (132) direction was done. Indications on the strip chart may be correlated to a position of the probe 11 and, therefore, to a position on the part being scanned.
- the scanning control software 181 and the signal processing software 182 may be integrated in numerically controlled machining programs (as shown in Figures 5 and 6 ).
- the test assembly 20 may include a panel 21 and a substructure 22.
- the substructure 22 may be smaller in size than the panel 21 and may include two holes 23.
- the substructure 22 may be positioned underneath the panel 21.
- the panel 21 may be the outer mold line skin of an aircraft fuselage or wing.
- the substructure 22 may be an edge of a flange of the substructure underneath the outer mold line skin or the wing including tooling holes.
- a C-scan 25 of the test assembly 20 (shown in Figures 2a and 2b ) is illustrated which was determined according to one embodiment of the present invention.
- the substructure 22 including the holes 23 may be clearly and with precision identified in the C-scan 25.
- Used for the C-scan 25 were an aluminum skin 21, an aluminum rib 22, and an eddy current probe 11 ( Figure 1 ) operated at 3 kHz.
- the scanning parameters may be optimized according to the materials of the panel 21 and the substructure 23, by selecting, for example, an appropriate probe 11 ( Figure 1 ) and an appropriate scanning frequency.
- the gantry motion system 30 may include a gantry 31, a bar 32, a pole 36, and a probe 11.
- the gantry motion system 30 may be used as a substructure scanning system.
- the gantry motion system 30 may provide precise positioning and movement of the probe 11 (also shown in Figure 1).
- Figure 1 shows the basic concept of precisely moving a probe 11 over an area 16 using a precision motion carriage 10. The same concept may be applied to the gantry motion system 30.
- the gantry 31 may be positioned over an assembly 37 to be scanned.
- the assembly 37 may include a substructure 38 and outer skins 39. The outer skins may be temporarily or permanently fastened to the substructure 38.
- the gantry 31 may cover a two-dimensional area 16.
- the bar 32 may be inserted into the gantry extending across the gantry 31 in y-direction 34 and being movable in x-direction 33.
- the pole 36 may be attached to the bar 32 such that the pole may move in y-direction 34 along the bar 32 and in z-direction 35.
- the pole 36 may include the probe 11 (also shown in Figure 1 ).
- the probe 11 may be an eddy current scanning sensor that may be used to detect metallic features of a substructure 38 underneath an outer skin 39 as frequently needed, for example, during the aircraft airframe assembly.
- the probe 11 may further be an ultrasonic scanning sensor that may be used to detect nonmetallic features of a substructure 38 underneath an outer skin 39.
- the probe 11 may further be any nondestructive scanning sensor.
- the probe 11 may be facing the assembly 37.
- the probe 11 may be moved towards the assembly 37 and away from the assembly 37 by moving the pole 36 in z-direction 34.
- the probe 11 may be moved precisely over the outer skin 39 of the assembly 27. Consequently, the substructure 38 including all features, such as edges of flanges, machined steps, and tooling holes, may be located with high accuracy.
- the obtained location coordinates of the substructure 38 may be used to control subsequent assembly processes, for example, of an aircraft airframe, such as drilling, reaming, machining or routing.
- the obtained location coordinates of the substructure 38 may be provided to a numerically controlled assembly machine to correct machine coordinates according to the location of the substructure 38.
- the robot motion system 40 may include a robot 41 having a robot arm 42.
- a probe 11 (also shown in Figure 1 ) may be attached to the robot arm 42.
- the probe 11 may be facing the assembly 37.
- the robot arm 42 may extend over an assembly 37 to be scanned.
- the robot arm 42 may position and move the probe 11 precisely over the outer skin 39 of the assembly 37 similar to the basic concept shown in Figure 1 and as described above.
- the probe 11 may be an eddy current scanning sensor that may be used to detect metallic features of a substructure 38 underneath an outer skin 39 as frequently needed, for example, during the aircraft airframe assembly.
- the probe 11 may further be an ultrasonic scanning sensor that may be used to detect nonmetallic features of a substructure 38 underneath an outer skin 39.
- the probe 11 may further be any nondestructive scanning sensor.
- the robot motion system 40 may be used as a substructure scanning system.
- the gantry motion system 30 and the robot motion system 40 may be examples for motion systems utilizing the basic concept of positioning and moving of a probe 11 as illustrated in Figure 1 and as described above.
- the probe 11 may be connected with a computer interface 18 via a controller box 17 (as shown in Figure 1 ).
- the controller box 17 may provide an alternating current to the probe 11, in the case, that the probe 11 is an eddy current scanning sensor.
- the probe 11 may generate eddy currents and sense changes in the eddy current field while being moved over the outer skin 39 of the assembly 37.
- the controller box 17 may receive signals that indicate changes in the eddy current and supply these signals to the computer interface 18.
- the computer interface 18 may include scanning control software 181 and signal processing software 182.
- the computer interface 18 may be connected with is connected with the controller box 17, the bar 32, and the pole 36.
- the scanning control software 181 may control the movement of the probe 11.
- the signal processing software 182 may generate images (such as the C-scan 25 shown in figure 2c ) from the scanned area 16 ( Figure 1 ).
- Both, the gantry motion system 30 and the robot motion system 40 may be integrated in a machine executing numerically controlled operations, such as drilling, trimming, or reaming (as shown in Figures 5 and 6 ). This may improve the product flow and automation of assembly processes, such as the aircraft airframe assembly, as well as provide more flexibility of assembly processes.
- the assembly process 50 may start with the assembly of a substructure 38 (shown in Figures 3 and 4 ) in step 51.
- outer skins 39 may be fitted and fastened onto the substructure 38.
- the outer skins 39 may be temporary or permanently fastened to the substructure 38 forming the assembly 37 (shown in Figures 3 and 4 ).
- the assembly 37 may be moved to an assembly machine (step 53) and may be placed on the machine work bed in relative position within the machine work zone (step 54).
- a substructure scanning system including a precision motion carriage 10 and a nondestructive scanning sensor 11 ( Figure 1 ) may be loaded in the machine and may be activated.
- the scanning control software 181 and the signal processing software182 may be included in the interface of the assembly machine.
- the scanning programs may be activated and executed by the substructure scanning system.
- Step 56 may further include steps 57, 58, 59, and 61.
- the probe 11 that is operated as a scanning sensor may be positioned according to an assembly based programming model in step 57.
- the probe 11 may be activated and moved over the outer skin 39 of the assembly 37 (as shown in Figure 3 and 4 ) to scan for features of the substructure 38 per program instructions (step 58).
- the signal processing software 182 may locate feature details of the substructure 38 and may extrapolate the true location dimensions in machine or assembly 37 coordinates in step 59.
- All points may be scanned repeatedly to increase accuracy and scan point data may be collected and saved (step 59).
- the determined true dimensions of the substructure 38 features may be saved for use in program corrections of the assembly machine (step 61).
- the substructure scanning system may be removed from the machine or deactivated in step 62.
- the numerically controlled programs for the assembly machine may be executed, for example, drilling, trimming, or reaming operations, while the scan point data may be used to correct program points and to align the assembly 37 and, therefore, the features of the substructure 38, relative to the machining tools.
- the assembly 37 may be moved from the machine work bed in step 64.
- the method 70 may include the step of sending a correction request from an assembly machine (step 71).
- the assembly machine may be a numerically controlled assembly machine, for example, for the assembly of aircraft airframes.
- a substructure scanning system may be used to position a probe 11 ( Figures 3 and 4 ) on the outer skin 39 of an assembly 37 ( Figures 3 and 4 ) and to move the probe 11 across a small area 16 ( Figure 1 ) using an x-y raster scan approach ( Figures 1 and 3 ).
- the probe 11 may be a scanning sensor.
- the probe 11 may be any nondestructive inspection sensor.
- the probe 11 may be preferably an eddy current scanning sensor.
- the method 70 may further include the step of collecting scanning data each time the probe 11 is moved by a small increment (step 73).
- a data file may be compiled containing position information and scanning data obtained with the probe 11 for the x-y field (area 16, Figure 1 ).
- the obtained data file may be analyzed to identify substructure 38 features defined by the sensor data.
- Step 76 may include computing assembly machine coordinates to identify location of substructure 38 features relative to assembly machine position. Machine coordinates orienting the assembly machine relative to the substructure 38 features may be returned in step 77.
- features of substructure 38 may be located with high accuracy meeting engineering tolerances.
- the scanning may be performed through the outer skin 39 eliminating the steps of removing the outer skin, manually mapping the substructure 38, and refastening the outer skin 39 to the substructure.
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Or Analyzing Materials By The Use Of Magnetic Means (AREA)
- Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
Description
- The present invention generally relates to nondestructive inspection methods and, more particularly, to detecting substructure using precision eddy current scanning.
- Automated assembly systems in the aerospace industry, for example, for airframe assembly of aircraft, generally employ some type of vision system for locating structure components and key features of components, such as edges of flanges, machined steps, and tooling holes. Knowledge of the exact location of these features is necessary, since these features are used to adjust numerically controlled programs for drilling holes or other machining operations, such as trimming or reaming, to maintain blueprint tolerances. Currently, it is often necessary to manually record where the substructure is located. In order to do this, the outer mold line skins, for example of a section of the fuselage or the wing, need to be removed to make the substructure underneath visible. Once a map of the substructure is created, the outer mold line skins are temporarily fastened to the structure and the created map of the substructure needs to be transferred to the skin. Since this step is performed while the assembly is in the machine bed, the flow time is impacted and the percentage of the machine time actually used for the intended function, such as drilling, is reduced.
- Eddy current as a nondestructive inspection process is commonly used in the aerospace industry to detect subsurface flaws or anomalies in conductive materials. The advantage of eddy current for nondestructive inspection is the ability to perform scanning through the outer skin material. Eddy current data can be collected using automated scanning systems to improve the quality of the measurements and to construct images of scanned areas. The most common type of scanning is line scanning where an automated system is used to push the probe at a fixed speed. The data is usually presented as a strip chart recording. The advantage of using a linear scanning system is that the probe is moved at a constant speed such that an indication on the strip chart can be correlated to a position on the part being scanned. Two-dimensional scanning systems are used to scan a two-dimensional area. This could be a scanning system that scans over a relatively flat area in an x -y raster mode. The data is typically displayed in a C -scan, which is a false-color plot of signal strength or phase angle shift as a function of position. Mobile automated scanners, such as MAUSĀ® IV and V developed by The Boeing Company, St. Louis, are generally used in the aerospace industry for nondestructive testing utilizing eddy current and ultrasonic waves. MAUS IV eddy current C-scans are used, for example, for corrosion detection or crack detection around fastener holes.
-
US 2003/192382 A1 discloses an apparatus that examines the internal structure of an object which reflects acoustic signals in the 1-200 MHz frequency range. The apparatus has an acoustic transducer that emits and receives the acoustic signals and an acoustic coupler to couple the transducer to the object, and the apparatus may scan over the surface of the object. -
US 2,785,592 discloses a magnetic position location and controlling probe and system. For the magnetic position location sensing coils are used. Eddy current is generated in plate material. -
US 2003/0212489 A1 discloses a magnetic indexer for locating a device producing a magnetic field in a blind or inaccessible position of a work piece. A device comprising a plurality of probes is positioned on a surface of the work piece and senses the magnetic field produced by the device in the blind or inaccessible position of the work piece. -
US 5,833,799 discloses an apparatus for thermoplastic welding together by fusing bonding an assembly of composite parts. The apparatus includes a weld skate having induction work coil and two pressure pads, one on each side of the coil in its direction of motion in operation. - The present invention has for its object to improve upon the above prior art apparatus.
- The present invention provides a method for detecting substructure, comprising the steps of non-destructively scanning an assembly (37) using a substructure scanning system (100) including a precision motion carriage (10), a first probe positioner movably coupled to said precision motion carriage such that it can move in a first direction relative to said precision motion carriage, a second probe positioner located above said first probe positioner and movably coupled to said precision motion carriage such that it can move in a second direction relative to said precision motion carriage, and a non-destructive scanning sensor (11) located in an opening of said first probe positioner and in an opening of said second probe positioner of said precision motion carriage; positioning said assembly (37) including a substructure (38) covered with an outer skin (39) under said substructure scanning system (100); positioning said scanning sensor (11) on said outer skin (39) of said assembly (37); moving said scanning sensor (11) over said outer skin (39) with said first probe positioner and said second probe positioner of said precision motion carriage (10), wherein moving said scanning sensor is accomplished by moving said first probe positioner and/or said second probe positioner such that said scanning sensor moves within the opening of the first probe positioner and/or within the opening of the second probe positioner; locating said substructure (38) through said outer skin (39) by evaluating signals received from said scanning sensor (11); controlling an assembly process (50) using said location of said substructure (38).
- The present invention provides for precisely detecting substructure using precision eddy current scanning. The present invention further uses a precision motion carriage that enables the location of substructure features within the engineering tolerances required. The present invention still further provides a method for the location of substructure features through an outer panel with sufficient accuracy to control assembly operations that may be used for, but is not limited to, the location of substructure features, such as edges of flanges, machined steps, or tooling holes, covered by outer mold line skins of an aircraft airframe.
- According to the present invention the substructure can be detected by any eddy current by sufficient accuracy to control assembly apparatus and meet engineering tolerances.
- These and other features, aspects and advantages of the present invention will become better understood with reference to the following drawings, description and claims.
-
-
Figure 1 is a schematic view of a dependent scanning system for use in one embodiment of the present invention; -
Figure 2a is a top view of a test specimen to be inspected according to one embodiment of the present invention; -
Figure 2b is a side view of a test to be inspected according to one embodiment of the present invention; -
Figure 2c is a C-scan of a test specimen determined using one embodiment of the present invention; -
Figure 3 is a perspective top view of a gantry motion system; -
Figure 4 is a perspective side view of a robot motion system; -
Figure 5 is a flow chart of an assembly process using the present invention; and -
Figure 6 is a flow chart of a method for machine coordinate correction using the present invention. - The following detailed description is of the best currently contemplated modes of carrying out the invention. The description is not to be taken in a limiting sense, but is made merely for the purpose of illustrating the general principles of the invention, since the scope of the invention is best defined by the appended claims.
- Broadly, the present invention provides for detecting substructure using nondestructive techniques. Contrary to the known prior art, an outer panel does not need to be removed to scan substructure that lies underneath the panel. Furthermore, by using the method for detecting substructure according to one embodiment of the present invention, substructure features can be located through the skin of a structure with sufficient accuracy to control assembly operations and meet engineering tolerances, which is not possible using prior art handheld devices or prior art nondestructive techniques. The method for detecting substructure as in one embodiment of the present invention may be used in the aerospace industry, for example, in the airframe assembly of aircraft. The method for detecting substructure further enables detection and location of substructure features, such as edges of flanges, machined steps, or tooling holes, that are located underneath the outer mold line skins, for example, of a fuselage or a wing of an aircraft.
- In one embodiment, the present invention uses eddy current to scan the outer mold line skin of an aircraft in order to detect substructure features underneath the skin. Since the removal of the skin is no longer required to create a map of the substructure, the steps of removing and refastening the skin, as currently needed using prior art methods, can be eliminated. Furthermore, by using eddy current for scanning a solid sheet of metallic or nonmetallic material, such as an aircraft airframe skin, edges and other features of metallic substructure located underneath the skin, on the side of the skin opposite to the scanning probe, can be located without removal of the airframe skin and in a nondestructive process. The advantage of eddy current for scanning is its ability to perform the scanning through the outer skin material. This will allow the temporary installation step for the outer mold line skins, for example, for a aircraft fuselage or wing, to take place before the assembly is presented to an automated machining system, for example, an automated drilling system, and will eliminate the intermediate step of skin installation after scanning as needed with prior art scanning methods. Using prior art scanning methods, the location of the substructure and the step of temporary fastening is performed while the assembly is situated in the machine bed.
- In one embodiment, the present invention uses a precision motion carriage that enables application of the eddy current scanning process with a high accuracy. By using the precision motion carriage as in one embodiment of the present invention, substructure features can be located with sufficient accuracy to control assembly operations, for example, numerically controlled programs for drilling holes, for trimming, or for reaming, and to meet engineering tolerances. Using prior art hand-held devices for detecting substructure does not provide this accuracy.
- An illustrative example provides a gantry motion system that moves the scanning sensor precisely over an area to be examined. In another illustrative example, a robot motion system moves the scanning sensor precisely over an area to be examined. Both motion systems enable the integration of the eddy current scanning process into numerically controlled machines, such as numerically controlled drilling machines, and, therefore, reduce the machine bed low time. Furthermore, the integration of the scanning process into the numerically controlled machining process enables instant machine coordinate correction without the need for manual actions, which provides more flexibility in the assembly process than prior art methods where the skins needs to be removed before the substructure features are visible, and where a map of the substructure needs to be created manually. Consequently, by using the method for detecting substructure using eddy current scanning as in one embodiment of the present invention, the product flow and automation of aircraft assemblies can be improved and the need for subassemblies and components can be reduced in comparison with prior art methods for locating substructure.
- Referring now to
Figure 1 , adependent scanning system 100 is illustrated for use in one embodiment of the present invention. Thedependent scanning system 100 may include aprecision motion carriage 10, aprobe 11, a controller box 17, and acomputer interface 18. Thedependent scanning system 100 may be used as a substructure scanning system. Thedependent scanning system 100 may enable application of eddy current scanning with a high accuracy. Thedependent scanning system 100 may be used as an attachment to an existing assembly machine, such as a machine executing numerically controlled operations, such as drilling, trimming, routing, machining or reaming. The assembly machine may locate thedependent scanning system 100 on a surface, for example, of a fuselage outer skin 31 (Figure 3 ), where thedependent scanning system 100 may perform the final precision scan in an x (122)-y (132) raster mode. Theprecision motion carriage 10 may include aprobe positioner 12, aprobe positioner 13, and aframe 14. Theframe 14 may have the shape of a square and may enclose a two-dimensional area 16. Theprobe positioner 12 may extend across theframe 14 inx-direction 122. Theprobe positioner 12 may include anopening 121 for guiding theprobe 11. Theprobe positioner 12 may be inserted into theframe 14 such that it may be moved in y-direction 132, within theframe 14. Theprobe positioner 13 may extend across theframe 14 in y-direction 132. Theprobe positioner 13 may include anopening 131 for guiding theprobe 11. Theprobe positioner 13 may be inserted in theframe 14 on top of theprobe positioner 12 and in a right angle to theprobe positioner 12. Theprobe positioner 13 may be moved inx-direction 122 within theframe 14. By positioning theprobe positioner 13 over theprobe positioner 12, theopening 131 and theopening 121 form awindow 15. Theprobe 11 may be inserted in thewindow 15. Using theprobe positioner 12 and theprobe positioner 13, theprobe 11 may be moved precisely over thearea 16 enclosed by theframe 14. By inserting theprobe 11 into thewindow 15, theprobe 11 may be accurately indexed. Theprobe 11 may be moved to scan a two-dimensional area 16 in an x (122)-y (132) raster mode. Theprobe 11 may be further moved within theopening 121 inx-direction 122 for one-dimensional line scanning. Theprobe 11 may still further be moved within theopening 131 in y-direction 132 for one-dimensional line scanning. Theprobe 11 may be an eddy current scanning sensor that may be used to detect metallic features of asubstructure 38 underneath an outer skin 39 (Figures 3 and4 ), as frequently needed, for example, during the aircraft airframe assembly. Theprobe 11 may further be an ultrasonic scanning sensor that may be used to detect nonmetallic features of asubstructure 38 underneath an outer skin 39 (Figures 3 and4 ). Theprobe 11 may further be any nondestructive scanning sensor. Using theprecision motion carriage 10 for scanning an assembly, such as test assembly 20 (Figures 2a and 2b ) or the assembly 37 (Figures 3 and4 ), may minimize changes in liftoff or fill factor resulting fromprobe 11 wobble or uneven surfaces, may provide repeatability of scanning results and high resolution mapping. - As illustrated in
Figure 1 , theprobe 11 may be connected with acomputer interface 18 via a controller box 17. The controller box 17 may provide an alternating current to theprobe 11. Theprobe 11 may generate eddy currents and sense changes in the eddy current field. The controller box 17 may receive signals that indicate changes in the eddy current and supply these signals to thecomputer interface 18. Thecomputer interface 18 may includescanning control software 181 andsignal processing software 182. Thecomputer interface 18 may be connected with akeyboard 183. Theprobe positioner 12 and theprobe positioner 13 may be connected with thecomputer interface 18. Thescanning control software 181 may control the movement of theprobe positioner 12 and theprobe positioner 13 and, therefore, of theprobe 11. Thesignal processing software 182 may generate an image (such as the C-scan 25,Figure 2c ) of the substructure 38 (Figures 3 and4 ). Thesignal processing software 182 may generate a C-scan 25 (as shown inFigure 2c ) if a two-dimensional area 16 was scanned in an x (122)- y (132) raster mode. The C-scan 25 may be a false-color plot of signal strength or phase angle shift as a function of the position of theprobe 11. Thesignal processing software 182 may generate a strip chart if a line scan in x (122) or y (132) direction was done. Indications on the strip chart may be correlated to a position of theprobe 11 and, therefore, to a position on the part being scanned. Thescanning control software 181 and thesignal processing software 182 may be integrated in numerically controlled machining programs (as shown inFigures 5 and6 ). - Referring now to
Figures 2a and 2b , a top view and a side view, respectively, of a test specimen to be inspected 20 are illustrated. Thetest assembly 20 may include apanel 21 and asubstructure 22. Thesubstructure 22 may be smaller in size than thepanel 21 and may include twoholes 23. Thesubstructure 22 may be positioned underneath thepanel 21. Thepanel 21 may be the outer mold line skin of an aircraft fuselage or wing. Thesubstructure 22 may be an edge of a flange of the substructure underneath the outer mold line skin or the wing including tooling holes. - Referring now to
Figure 2c , a C-scan 25 of the test assembly 20 (shown inFigures 2a and 2b ) is illustrated which was determined according to one embodiment of the present invention. As can be seen, thesubstructure 22 including theholes 23 may be clearly and with precision identified in the C-scan 25. Used for the C-scan 25 were analuminum skin 21, analuminum rib 22, and an eddy current probe 11 (Figure 1 ) operated at 3 kHz. The scanning parameters may be optimized according to the materials of thepanel 21 and thesubstructure 23, by selecting, for example, an appropriate probe 11 (Figure 1 ) and an appropriate scanning frequency. - Referring now to
Figure 3 , agantry motion system 30 is illustrated. Thegantry motion system 30 may include agantry 31, abar 32, apole 36, and aprobe 11. Thegantry motion system 30 may be used as a substructure scanning system. Thegantry motion system 30 may provide precise positioning and movement of the probe 11 (also shown inFigure 1). Figure 1 shows the basic concept of precisely moving aprobe 11 over anarea 16 using aprecision motion carriage 10. The same concept may be applied to thegantry motion system 30. Thegantry 31 may be positioned over anassembly 37 to be scanned. Theassembly 37 may include asubstructure 38 andouter skins 39. The outer skins may be temporarily or permanently fastened to thesubstructure 38. Thegantry 31 may cover a two-dimensional area 16. Thebar 32 may be inserted into the gantry extending across thegantry 31 in y-direction 34 and being movable inx-direction 33. Thepole 36 may be attached to thebar 32 such that the pole may move in y-direction 34 along thebar 32 and in z-direction 35. Thepole 36 may include the probe 11 (also shown inFigure 1 ). Theprobe 11 may be an eddy current scanning sensor that may be used to detect metallic features of asubstructure 38 underneath anouter skin 39 as frequently needed, for example, during the aircraft airframe assembly. Theprobe 11 may further be an ultrasonic scanning sensor that may be used to detect nonmetallic features of asubstructure 38 underneath anouter skin 39. Theprobe 11 may further be any nondestructive scanning sensor. Theprobe 11 may be facing theassembly 37. Theprobe 11 may be moved towards theassembly 37 and away from theassembly 37 by moving thepole 36 in z-direction 34. By moving thebar 32 inx-direction 33 and by moving thepole 36 in y-direction 34 along thebar 32, theprobe 11 may be moved precisely over theouter skin 39 of the assembly 27. Consequently, thesubstructure 38 including all features, such as edges of flanges, machined steps, and tooling holes, may be located with high accuracy. The obtained location coordinates of thesubstructure 38 may be used to control subsequent assembly processes, for example, of an aircraft airframe, such as drilling, reaming, machining or routing. The obtained location coordinates of thesubstructure 38 may be provided to a numerically controlled assembly machine to correct machine coordinates according to the location of thesubstructure 38. - Referring now to
Figure 4 , arobot motion system 40 is illustrated. Therobot motion system 40 may include arobot 41 having arobot arm 42. A probe 11 (also shown inFigure 1 ) may be attached to therobot arm 42. Theprobe 11 may be facing theassembly 37. Therobot arm 42 may extend over anassembly 37 to be scanned. Therobot arm 42 may position and move theprobe 11 precisely over theouter skin 39 of theassembly 37 similar to the basic concept shown inFigure 1 and as described above. Theprobe 11 may be an eddy current scanning sensor that may be used to detect metallic features of asubstructure 38 underneath anouter skin 39 as frequently needed, for example, during the aircraft airframe assembly. Theprobe 11 may further be an ultrasonic scanning sensor that may be used to detect nonmetallic features of asubstructure 38 underneath anouter skin 39. Theprobe 11 may further be any nondestructive scanning sensor. Therobot motion system 40 may be used as a substructure scanning system. - The
gantry motion system 30 and therobot motion system 40 may be examples for motion systems utilizing the basic concept of positioning and moving of aprobe 11 as illustrated inFigure 1 and as described above. In bothSystems probe 11 may be connected with acomputer interface 18 via a controller box 17 (as shown inFigure 1 ). The controller box 17 may provide an alternating current to theprobe 11, in the case, that theprobe 11 is an eddy current scanning sensor. Theprobe 11 may generate eddy currents and sense changes in the eddy current field while being moved over theouter skin 39 of theassembly 37. The controller box 17 may receive signals that indicate changes in the eddy current and supply these signals to thecomputer interface 18. Thecomputer interface 18 may includescanning control software 181 andsignal processing software 182. Thecomputer interface 18 may be connected with is connected with the controller box 17, thebar 32, and thepole 36. Thescanning control software 181 may control the movement of theprobe 11. Thesignal processing software 182 may generate images (such as the C-scan 25 shown infigure 2c ) from the scanned area 16 (Figure 1 ). Both, thegantry motion system 30 and therobot motion system 40 may be integrated in a machine executing numerically controlled operations, such as drilling, trimming, or reaming (as shown inFigures 5 and6 ). This may improve the product flow and automation of assembly processes, such as the aircraft airframe assembly, as well as provide more flexibility of assembly processes. - Referring now to
Figure 5 , a flow chart of anassembly process 50 is illustrated using the present invention. Theassembly process 50 may start with the assembly of a substructure 38 (shown inFigures 3 and4 ) instep 51. Instep 52,outer skins 39 may be fitted and fastened onto thesubstructure 38. Theouter skins 39 may be temporary or permanently fastened to thesubstructure 38 forming the assembly 37 (shown inFigures 3 and4 ). Theassembly 37 may be moved to an assembly machine (step 53) and may be placed on the machine work bed in relative position within the machine work zone (step 54). Instep 55, a substructure scanning system including aprecision motion carriage 10 and a nondestructive scanning sensor 11 (Figure 1 ) may be loaded in the machine and may be activated. Thescanning control software 181 and the signal processing software182 (Figure 2 ) may be included in the interface of the assembly machine. Instep 56, the scanning programs may be activated and executed by the substructure scanning system.Step 56 may further includesteps probe 11 that is operated as a scanning sensor may be positioned according to an assembly based programming model instep 57. Theprobe 11 may be activated and moved over theouter skin 39 of the assembly 37 (as shown inFigure 3 and4 ) to scan for features of thesubstructure 38 per program instructions (step 58). Thesignal processing software 182 may locate feature details of thesubstructure 38 and may extrapolate the true location dimensions in machine orassembly 37 coordinates instep 59. All points may be scanned repeatedly to increase accuracy and scan point data may be collected and saved (step 59). The determined true dimensions of thesubstructure 38 features may be saved for use in program corrections of the assembly machine (step 61). When all scan points are completed for a series of numerically controlled programs, the substructure scanning system may be removed from the machine or deactivated instep 62. InStep 63, the numerically controlled programs for the assembly machine may be executed, for example, drilling, trimming, or reaming operations, while the scan point data may be used to correct program points and to align theassembly 37 and, therefore, the features of thesubstructure 38, relative to the machining tools. After the machine completes all numerically controlled programs instep 63, theassembly 37 may be moved from the machine work bed instep 64. - Referring now to
Figure 6 , a flow chart of amethod 70 for machine coordinate correction is illustrated using the present invention. Themethod 70 may include the step of sending a correction request from an assembly machine (step 71). The assembly machine may be a numerically controlled assembly machine, for example, for the assembly of aircraft airframes. Instep 72, a substructure scanning system may be used to position a probe 11 (Figures 3 and4 ) on theouter skin 39 of an assembly 37 (Figures 3 and4 ) and to move theprobe 11 across a small area 16 (Figure 1 ) using an x-y raster scan approach (Figures 1 and3 ). Theprobe 11 may be a scanning sensor. Theprobe 11 may be any nondestructive inspection sensor. Theprobe 11 may be preferably an eddy current scanning sensor. Themethod 70 may further include the step of collecting scanning data each time theprobe 11 is moved by a small increment (step 73). Instep 74, a data file may be compiled containing position information and scanning data obtained with theprobe 11 for the x-y field (area 16,Figure 1 ). In the followingstep 75, the obtained data file may be analyzed to identifysubstructure 38 features defined by the sensor data.Step 76 may include computing assembly machine coordinates to identify location ofsubstructure 38 features relative to assembly machine position. Machine coordinates orienting the assembly machine relative to thesubstructure 38 features may be returned instep 77. By applying the basic concept of the precision motion carriage 10 (as shown inFigure 1 ) to substructure scanning systems, usingprobes 11 for nondestructive scanning, features of substructure 38 (Figures 3 and4 ) may be located with high accuracy meeting engineering tolerances. Furthermore, by using eddy current for detecting substructure the scanning may be performed through theouter skin 39 eliminating the steps of removing the outer skin, manually mapping thesubstructure 38, and refastening theouter skin 39 to the substructure. Even though the method for detecting substructure using precision eddy current scanning has been described mainly for application in the aircraft airframe assembly process, other applications, for example, in the automobile industry, may be possible. - It should be understood, of course, that the foregoing relates to exemplary embodiments of the invention and that modifications may be made without departing from the scope of the invention as set forth in the following claims.
Claims (8)
- A method for detecting substructure, comprising the steps of:non-destructively scanning an assembly (37) using a substructure scanning system (100) including a precision motion carriage (10), wherein the precision motion carriage (10) includes a first probe positioner (13), a second probe positioner (12) and a frame (14) used to enclose a two-dimensional area, and a non-destructive scanning sensor (11), wherein the first probe positioner (13) is inserted into the frame (14), wherein the second probe positioner (12) is inserted in the frame (14) and located above said first probe positioner (13) and, wherein the scanning sensor (11) is inserted into a window (15) formed by a first opening (131) of said first probe positioner (13) and a second opening (121) of said second probe positioner (12);positioning said assembly (37) including a substructure (38) covered with an outer skin (39) under said substructure scanning system (100);positioning said scanning sensor (11) on said outer skin (39) of said assembly (37);moving said scanning sensor (11) over said outer skin (39) across said two-dimensional area using said first probe positioner (13) and said second probe positioner (12) of said precision motion carriage (10) in an x-y raster mode, wherein said first probe positioner (11) is moveable in an x-direction (122) and said second probe positioner (12) is movable in a y-direction (132) within said frame (14), wherein said scanning sensor (11) is moved by moving said first probe positioner (13) and/or said second probe positioner (12) such that said scanning sensor (11) respectively moves within said second opening (121) of the second probe positioner (12)and/or within said first opening (131) of said first probe positioner (13);locating said substructure (38) through said outer skin (39) by evaluating signals received from said scanning sensor (11);controlling an assembly process (50) using said location of said substructure (38).
- The method for detecting substructure of claim 1, further comprising the steps of:nondestructively scanning said assembly (37) using an eddy current scanning sensor; and detecting metallic features of said substructure (38).
- The method for detecting substructure of any of claims 1 or 2, further comprising the steps of:nondestructively scanning said assembly (37) using an ultrasonic scanning sensor; anddetecting nonmetallic features of said substructure (38).
- The method for detecting substructure of any one or more claims 1-3, further comprising the step of:scanning a two-dimensional area (16) of said outer skin (39) in an x-y raster mode with said scanning sensor (11).
- The method for detecting substructure of any one or more claims 1-4, further comprising the step of:line scanning said outer skin (39) in one dimension with said scanning sensor (11).
- The method for detecting substructure of any one or more of claims 1, 2, 4 or 5, further comprising the steps of:connecting said scanning sensor (11) with a controller box (17);connecting said controller box (17) with a computer interface (18);feeding an alternating current to said scanning sensor (11) using said controller box (17);generating an eddy current with said scanning sensor (11);sensing changes in the eddy current field with said scanning senor (11);receiving signals indicating said changes in the eddy current field with said controller box (17); andsupplying said signals to said computer interface (18) with said controller box (17).
- The method for detecting substructure of any one or more claims 1-6, further comprising the steps of:controlling the position and movement of said scanning sensor (11) with scanning control software (181) included in said computer interface (18); andgenerating an image of said substructure (38) using signal processing software (182) included in said computer interface (18).
- The method for detecting substructure of any one or more claims 1-7, further comprising the step of:integrating said substructure scanning system (100) into a numerically controlled assembly machine.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/975,328 US7292029B2 (en) | 2004-10-28 | 2004-10-28 | Method for detecting substructure |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1657545A1 EP1657545A1 (en) | 2006-05-17 |
EP1657545B1 true EP1657545B1 (en) | 2017-06-21 |
Family
ID=35572649
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05077399.3A Not-in-force EP1657545B1 (en) | 2004-10-28 | 2005-10-19 | Method for detecting substructure |
Country Status (2)
Country | Link |
---|---|
US (2) | US7292029B2 (en) |
EP (1) | EP1657545B1 (en) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7292029B2 (en) * | 2004-10-28 | 2007-11-06 | The Boeing Company | Method for detecting substructure |
US7898246B2 (en) | 2007-08-01 | 2011-03-01 | The Boeing Company | Method and apparatus for nondestructive inspection of interwoven wire fabrics |
FR2947633B1 (en) * | 2009-07-02 | 2012-04-13 | Snecma | DEVICE FOR NON-DESTRUCTIVE CONTROL OF A PIECE |
US9032602B2 (en) * | 2011-07-15 | 2015-05-19 | The Boeing Company | Methods and systems for in-process quality control during drill-fill assembly |
FR2980267B1 (en) * | 2011-09-21 | 2013-10-04 | Eads Europ Aeronautic Defence | FOURCAULT CURRENT MEASURING DEVICE AND MACHINE FOR COUNTERPILLING A COMPLEX STRUCTURE COMPRISING SUCH A DEVICE |
US20130115529A1 (en) * | 2011-11-08 | 2013-05-09 | U.S. Government As Represented By The Secretary Of The Army | Electrolyte for metal/air battery |
FR3033895B1 (en) * | 2015-03-18 | 2018-08-31 | Airbus Operations | VERIFICATION TOOL FOR VERIFYING THE STATE OF A VENEER LAYER OF AN ELEMENT |
CN105842335A (en) * | 2016-03-25 | 2016-08-10 | 大čæēå·„å¤§å¦ | Multi-parameter-integrated ferromagnetic metal material micro-crack detection method |
CN106053592B (en) * | 2016-06-13 | 2018-04-20 | ę²³ęµ·å¤§å¦ | Real bridge welding seam scanner and its scan method |
CN109642862B (en) * | 2016-07-01 | 2021-12-24 | ä¼å©čÆŗęÆå·„å ·å¶åęéå ¬åø | Integrated system and method for in-situ 3-axis scanning and detecting defects in objects under static and cyclic testing |
US10518243B2 (en) * | 2016-12-15 | 2019-12-31 | Altria Client Services Llc | Portion of an electronic vaping device formed of an oxygen sequestering agent |
CN106643859B (en) * | 2016-12-27 | 2018-12-14 | ęå°č”份ęéå ¬åø | PIN point communication check device |
JP2018124154A (en) * | 2017-01-31 | 2018-08-09 | å¦ę ”ę³äŗŗäŗ島č²č±ä¼ | C-scope imaging system of eddy current flaw detection result for fatigue crack of steel bridge welded edge |
FR3090586A1 (en) * | 2018-12-20 | 2020-06-26 | Airbus Operations | System and method for determining the spacing between two rooms using eddy current sensors |
US20230288373A1 (en) * | 2022-02-28 | 2023-09-14 | Verifi Technologies, Llc | Eddy current probe and method for determining ply orientation using eddy current and ultrasonic probes |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20030212489A1 (en) * | 2002-05-09 | 2003-11-13 | Georgeson Gary E. | Magnetic indexer for high accuracy hole drilling |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2785592A (en) | 1952-12-23 | 1957-03-19 | Shell Dev | Magnetic position locating and controlling probe and system |
US4774842A (en) | 1986-02-19 | 1988-10-04 | Mcdonnell Douglas Corporation | Hand-held apparatus to nondestructively test subsurface structure |
US5660669A (en) | 1994-12-09 | 1997-08-26 | The Boeing Company | Thermoplastic welding |
AU2002222956A1 (en) | 2000-07-14 | 2002-01-30 | Lockheed Martin Corporation | System and method for locating and positioning an ultrasonic signal generator for testing purposes |
US6973832B2 (en) | 2002-02-08 | 2005-12-13 | Metscan Technologies, Llc | Acoustic coupling with a fluid bath |
US7292029B2 (en) * | 2004-10-28 | 2007-11-06 | The Boeing Company | Method for detecting substructure |
-
2004
- 2004-10-28 US US10/975,328 patent/US7292029B2/en not_active Expired - Fee Related
-
2005
- 2005-10-19 EP EP05077399.3A patent/EP1657545B1/en not_active Not-in-force
-
2007
- 2007-10-08 US US11/868,936 patent/US20080024125A1/en not_active Abandoned
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20030212489A1 (en) * | 2002-05-09 | 2003-11-13 | Georgeson Gary E. | Magnetic indexer for high accuracy hole drilling |
Also Published As
Publication number | Publication date |
---|---|
EP1657545A1 (en) | 2006-05-17 |
US20060091880A1 (en) | 2006-05-04 |
US7292029B2 (en) | 2007-11-06 |
US20080024125A1 (en) | 2008-01-31 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1657545B1 (en) | Method for detecting substructure | |
US7508971B2 (en) | Inspection system using coordinate measurement machine and associated method | |
EP2400297B1 (en) | Inspection system and associated method | |
US7253908B2 (en) | Non-destructive inspection using laser profiling and associated method | |
US8365602B2 (en) | Weld seam tracking system using phased array ultrasonic devices | |
EP2097787B1 (en) | Automated imaging of part inconsistencies | |
EP2162807B1 (en) | System and method for automated inspection of large-scale part | |
US5537876A (en) | Apparatus and method for nondestructive evaluation of butt welds | |
US20100316458A1 (en) | Automated Material Removal in Composite Structures | |
CA2580278C (en) | Rivet rotating probe | |
EP3781937B1 (en) | A robot system and method for non-destructive testing | |
JP3679384B2 (en) | Drilling device | |
CN114740084A (en) | Detection method and system for steel surface coating | |
CN115656325A (en) | Lamb wave based internal weld width detection method and device for lap joint laser welding head | |
Liu et al. | Industrial robot-based system design of thickness scanning measurement using ultrasonic | |
CN113523642A (en) | Welding seam detects and welding set | |
Novak et al. | A high resolution capacitive imaging sensor for manufacturing applications | |
RU38148U1 (en) | INSTALLATION FOR AUTOMATED RAIL CONTROL | |
CN118275542B (en) | Diffraction time difference ultrasonic scanning method and scanning frame for large-thickness butt weld | |
Schwarzkopf | Overview and Comparison of Noncontacting and Traditional Contacting Extensometers | |
Malyy et al. | Development of an Algorithm for the Movement and Adjusting Measuring Transducers of an Automated Non-Destructive Testing System | |
CN118518763A (en) | Method and system for associating test data of a part under test with a finished product coordinate system | |
JPS63187185A (en) | Measurement of position of back plate | |
Schmitt et al. | Machine vision and ultrasonic supported measuring and monitoring concept for economical quality enhancement in small batch production | |
Arnaud et al. | Design of a System of Inspection Assisted by Microprocessor (SIAM) for Adhesive Bonded Composite Structures |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
17P | Request for examination filed |
Effective date: 20060502 |
|
17Q | First examination report despatched |
Effective date: 20060623 |
|
AKX | Designation fees paid |
Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20170213 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 903412 Country of ref document: AT Kind code of ref document: T Effective date: 20170715 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602005052159 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20170621 Ref country code: FR Ref legal event code: PLFP Year of fee payment: 13 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170922 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 903412 Country of ref document: AT Kind code of ref document: T Effective date: 20170621 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170921 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20171025 Year of fee payment: 13 Ref country code: DE Payment date: 20171027 Year of fee payment: 13 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20171021 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20171027 Year of fee payment: 13 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602005052159 Country of ref document: DE |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |
|
26N | No opposition filed |
Effective date: 20180322 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20171019 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20171031 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20171031 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20171031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20171031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20171019 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 602005052159 Country of ref document: DE |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20181019 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20051019 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190501 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20181031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CY Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20170621 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20181019 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20170621 |